Compressor with segmented inner shroud for an axial turbine engine
作者： Stephane Hiernaux
DOI:
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摘要: The invention relates to an assembly for a turbojet engine. comprises outer shroud (36) and inner (32) being segmented comprising circumferential clearances between the segments thereof; annular row of stator vanes connecting shroud; drive with reduction ratio, which is intended be coupled fan; loop (34) cooling lubricating drive, configured heat up at least during operation turbine engine such as circumferentially reduce segments. further brings forward method used controlling
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